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1、US 20140319269A1(i9) United States(12) Patent Application PublicationScarr et al.(io) Pub. No.: US 2014/0319269 AlOct. 30,2014(43) Pub. Date:(54)INNER COWL STRUCTURE FOR AIRCRAFT TURBINE ENGINEPublication Classification(51)Int.Cl. F04D 29/40 B64D 29/02 B64D 29/06U.S. Cl.CPC .(71)Applicant: MRA Syste

2、ms, Inc., (US)(2006.01)(2006.01)(2006.01)(72)Inventors: Antony Brett Scarr, Bel Air, MD (US); Thomas Joseph Weir, Lutherville, MD (US); Allen Madsen Woolley, Rose Hill, KS (US); Carol Marie Janzon, Abingdon, MD (US)(52)F04D 29/40 (2013.01); B64D 29/06(2013.01); B64D 29/02 (2013.01)USPC244/54; 415/18

3、2.1ABSTRACT(57)(73)Assignee: MRA Systems, Inc., Baltimore, MD (US)An inner cowl structure for circumscribing at least a portion of a jet engine extending from an aircraft includes an apron configured to mount directly to the engine independent ofthe pylon and overly an upper portion of the jet engin

4、e, and an inner body configured to circumscribe a portion of the jet engine not circumscribed by the apron.(21)Appl.No.: 13/862,941(22)Filed:Apr. 15, 2013fjgl/10-.s;.Patent Application PublicationOct. 30, 2014 Sheet 1 of 5US 2014/0319269 A1Patent Application PublicationOct. 30, 2014 Sheet 2 of 5US 2

5、014/0319269 A1Patent Application PublicationOct. 30, 2014 Sheet 3 of 5US 2014/0319269 A1Patent ApplicationPublicationOct. 30, 2014 Sheet 4 of 5US 2014/0319269 A1Patent ApplicationPublicationOct. 30, 2014 Sheet 5 of 5US 2014/0319269 A15870US 2014/0319269 A1Oct. 30, 20141INNER COWL STRUCTURE FOR AIRCR

6、AFT TURBINE ENGINEbody defines a hoop structure that is structurally independent ofthe pylon and completely circumscribes at least a portion of the jet engine.BACKGROUND OF THE INVENTION0001 Turbine engines, and particularly gas turbine engines, also known as combustion turbine engines, are rotary e

7、ngines that extract energy from a flow of combusted gases passing through the engine onto a multitude ofturbine blades. Gas turbine engines have been used for land and nautical locomotionandpowergeneration, butaremostcom monly used for aeronautical applications such as for air planes. In airplanes,

8、gas turbine engines are used for propul sion ofthe aircraft.0002 The engine is attached to a wing by a pylon, typi cally a metal armthatjoins the engine to the wing or fuselage ofthe aircraft. Through pumps and feed tubes in the pylons, fuel is relayed from wing tanks to the engine. Additionally, el

9、ectricalpowergeneratedbytheengine, aswellashydraulic lines and air management system ducts, control system wir ing, etc. are routed between the aircraft and engine through wires and piping also contained in the pylons. The engine is containedwithinexternalcasings, calledcowls. Thesecowls typically f

10、orm the inner wall of a fan duct on aircraft appli cations. Theseenginecowlsaresupportedinpartbythepylon and in part by theengine.0003 Conventional cowl arrangements include the inner and outer cowls that are structurally attached to each other via bifurcation walls and beams that permit hinged open

11、ing and closing of the cowls for engine access, and in some cases permit sliding ofthe outer cowl for thrust reverser operations. In other arrangements the inner cowl remains independent from the outer cowl (i.e. has no direct structural attachment between the cowls). In this case the inner cowling

12、covers the jet engine and has either a fixed frame structure with many access panels to provide engine access or hinged opening forward doors with a sliding aft cowl section that may be moved to provide access for maintenance of the jet engine.BRIEF DESCRIPTION OF THE DRAWINGS0006 In the drawings:00

13、07 FIG. 1 is a cross-sectional side view of a typical gas turbine engine, cowling, pylon, and wing, according to one embodiment of the invention.0008 FIG. 2 is a perspective view of the cowling and apron, according to one embodiment of the invention. 0009 FIG. 3 is a partial sectional view taken alo

14、ng line 3-3 of FIG. 1 showing the hoop structure.0010 FIG. 4 is a perspective view ofthe apron structure. 0011 FIG. 5 is a partial sectional view showing the apron mounting brackets.DESCRIPTION OF EMBODIMENTS OF THE INVENTION0012 The invention may be implemented in any environ ment using a gas turbi

15、ne engine that provides propulsive force for aircraft. Additionally, embodiments ofthis description is also applicable to a turbine engine providing a power genera tion and/or providing both a driving force and power genera tion. Further, while embodiments of this description is directed toward a je

16、t engine aircraft environment, the inven tion is applicable in any environment using a turbine engine that also uses cowls.0013 FIG. 1 is a schematic cross-sectional diagram of a gas turbine engine 10 for an aircraft. The engine 10 includes, in downstream serial flow relationship, a fan section 12 i

17、ncluding a fan 14, a booster or low pressure (LP) compressor 16, a high pressure (HP) compressor 18, a combustion section 20, a HP turbine 22, and a LP turbine 24. An HP shaft or spool 26 drivingly connects HP turbine 22 to HP compressor 18 and an LP shaft or spool 28 drivingly connects LP turbine 2

18、4 to LP compressor 16 and fan 14. HP turbine 22 includes an HP turbine rotor 30 having turbine blades 32 mounted at a periph ery of rotor 30. Blades 32 extend radially outwardly from blade platforms 34 to radially outer blade tips 36.0014 The engine 10 is shown mounted to the pylon assembly 38, at a

19、 pylon primary structure 40, by both aft and fore engine mounts 42. The pylon assembly 38, as illustrated, further secures to the aircraft wing 44 in a vertical orientation, but may be secured at alternate positions ofthe aircraft, such as to the fuselage in a horizontal orientation.0015 Theengine 1

20、0 furtherincludes anoutercowl 46 and aninner cowl 48, each having smooth surfaces to reduce the drag ofairpassing inside oroutsidethe engine 10 in flight. Theoutercowl 46 encirclesatleastaportionoftheinnercowl 48 and the engine 10. The pylon assembly 38 further com prises bifurcationwalls 50, connec

21、tedto andextending from the pylonassembly 38 towardthe inner cowl 48, defininga gap 52 which is sealed to preserveeffectivefanairpassage alongthefanductbetweentheinnercowl48 andoutercowl 46.0016 Also illustrated are a multitude of connector lines 54, such as hydraulic lines, electrical lines and byp

22、ass air lines, extending from the engine 10 through the bifurcation walls 50 into the pylon assembly 38. These lines 54 coupling the engine 10 to subsystems necessary for operation, such as fuel pumps and flight control computers.BRIEF DESCRIPTION OF THE INVENTION0004In one aspect, an inner cowl str

23、ucture for circum scribing at least a portion of a jet engine having at least one engine mount coupled to an engine pylon extending from an aircraft wing, the inner cowl structure includes an apron con figured to mount directly to the engine independent of the pylon and overly an upper portion of th

24、e jet engine, and an inner body configured to circumscribe a portion of the jet engine not circumscribed by the apron, wherein the inner cowl body is coupled to the apron such that the resulting combination of the coupled apron and inner cowl body defines a hoop structure that is structurally indepe

25、ndent ofthe pylon and completely circumscribes at least a portion of the jet engine.0005 In another aspect, an aircraft assembly including a wing, an engine pylon mounted to the wing, a jet engine mounted to the engine pylon with at least one engine mount connection, and an inner cowl structure. The

26、 inner cowl struc ture further includes an apron mounted directly to the engine independent of the pylon and overlying an upper portion of the jet engine, and an inner cowl body configured to circum scribe a portion of the jet engine not circumscribed by the apron. The inner cowl body is coupled to

27、the apron such that the resulting combination ofthe coupled apron and inner cowlUS 2014/0319269 A1Oct. 30, 201420017 Turning now to FIG. 2, the inner cowl 48 comprises an apron structure 58, two side forward cowl doors 60, and an aft cowl door 62 circumscribing at least a portion of the engine 10. A

28、lternate configurations of cowling are envi sioned. The apron 58 overlies an upper portion ofthe engine 10 while the forward cowl doors 60 and aft cowl door 62 collectively circumscribe the remaining portion ofthe engine 10 not overlied by the apron 58. The forward cowl doors 60 hingedly open wherea

29、s the aft cowl door 62 slidably opens. 0018 As shown in FIG. 3, the assembled apron 58 and cowl doors 60, 62 create a continuous hoop-wise structure that extends along the axial length of the inner cowl 48. As illustrated, the apron 58 further comprises a sealing com poundattheedges ofgap 52 between

30、thebifurcationwalls 50 and the apron 58. One example of the sealing compound is aero seal 64; however, other compounds that provide a soft, flexible seal between suchinterfaces are envisioned. Also as shown, the forward cowl doors 60 each circumscribe a mir- rored-oppositesideportionoftheforwardengi

31、ne 10 suchthat the lower edges of the doors 60 meet each one another at the lowest point of the inner cowl 48.0019 Turning now to FIG. 4, the apron 58 comprises supporthinges 66 andrailings 68 foractuatingthecowldoors 60, 62. The forwardcowl doors 60 couple to the apron 58 via thehinges 66andareconf

32、iguredsuchthatthehinges 66create a pivot point, allowing the doors 60 to swing up and away from the engine 10 during maintenance. Likewise, the rail ings 68 allowforcoupling ofthe aftcowl door 62 to theapron 58 such that the door 62 may be translated axially, for example by sliding, along the length

33、 of the engine 10 from a fore position to an aft position, relative to the apron 58 and engine 10, during maintenance. In the present configuration, both the hinges 66 and the railings 68 are made from suitable materials robust enough to support the loads oftheir respec tive cowl doors 60, 62 during

34、 flight or maintenance opera tions.0020 Theapron 58 yetfurthercomprises acollar 72 that abutsthepylonassembly 38. Theapron 58 yetfurthercom prises at least one opening permitting a pass through connec tionto theengine 10. Asillustrated, thecollar 72 includes a collar opening 74, wherein the engine m

35、ount 42 passes throughto securetheengine 10 tothepylonprimarystructure40. The apron 58 is shownhaving additional openings 76 for the connector lines 54, however, it is envisioned that addi tional connections may be permitted to pass through the col lar opening 74.0021 The collar 72 further comprises

36、 a seal structure 78 corresponding to and circumscribing the collar opening 74. The seal structure 78 is configured in such a way that when the collar 72 abuts the pylon assembly 38, the seal structure 78 seals the collar opening 74 relative to the pylon assembly 38. The seal structure 78 may compri

37、se any suitable soft, flexible material able to form a substantially air and weather-proof seal.0022 Turning to FIG. 5, the apron 58 further comprises apron mounts 70 for structurally coupling the apron 58 to the engine 10. In this sense, the engine 10 supports the weight of the inner cowl 48, which

38、 is structurally independent of the pylon assembly 38. The apron mounts 70 comprise materials suitable to support the combined weight of the apron 58, forward cowl doors 60, and the aft cowl door 62, as well as any transient forces applied to the inner cowl 48 during flight or maintenance operations

39、. Alternate configurations ofapron mounts 70 are envisioned.0023 During flight operation, an inner cowl 48 circum scribing an engine 10 providing thrust to an aircraft, will experience gravitational and displacement loads. The gravi tational loads, or weight ofthe inner cowl 48, are carried from the

40、 cowl doors 60, 62, through the apron 58, to the engine 10 by the apron mounts 70. The hoop-wise continuous structure of the apron 58 and cowl doors 60, 62 provide a structurally efficient design for carrying the weight of the inner cowling 48.0024 The displacement loads acting upon the inner cowl 4

41、8 originate, mainly, from airstream effects, turbulence, and vibration of the engines 10. While the apron mounts 70 may provide both structural stiffness and damping effects, the inner cowl 48 is still slightly displaced relative to the pylon assembly 38. This displacement is accounted for at the in

42、ter face to the pylon assembly 38, by the aero seal 64 at the apron and bifurcation walls 50 and the seal structure 78 at the collar 72 and the pylon assembly 38. The soft, flexible material of each seal 64,78 allows for displacement without separation at each interface. Furthermore, the hoop-wise c

43、ontinuous struc ture of the apron 58 and cowl doors 60, 62 provide a struc turally efficient design forwithstanding warping or deflection under displacement loads.0025 Many other possible embodiments and configura tions in addition to that shown in the above figures are con templated by the present

44、disclosure. For example, one embodiment of the invention contemplates an apron 58 that further circumscribes the engine 10 or extends further axially, removing or reducing the need for additional cowl doors 60,62. Furthermore, a multitude of embodiments having alter nate cowl door 60, 62 designs may

45、 be employed, so long as the inner cowl 48 is structurally anchored to an apron 58 in each such embodiment. Additionally, the design and place ment of the various components may be rearranged such that a number of different configurations could be realized. 0026 The embodiments disclosed herein prov

46、ide an inner cowl structure for a turbine engine. One advantage that may be realized in the above embodiments is that the above described embodiments have superior complexity and lower costdesignadvantagesovertheconventionaltypeinnercowl structures.Withtheproposedapronmountingstructureabout the engi

47、ne, ahigh structural integrity oftheinnercowl canbe achieved due to the hoop-wise strength, while structurally isolatingthecowlingfromany directconnectiontothepylon or pylonbracket. Moreover, giventhatthe dominant loading cases of the inner cowl is pressure driven, the hoop-wise continuous structure

48、 ofthe described embodiments are espe cially efficient.0027 Anotheradvantagethatmay be realizedintheabove embodiments is that the inner cowl provides a means to minimizethe thermal effect ofengine heat onthe lower floor of the pylon due to the structural separation and isolation barrierbetweentheapr

49、onandthe bifurcationwalls. Creating this isolation barrier also decreases the engine fire zone vol ume, benefitting other subsystems suchas fire detection and suppression.0028 Additionally, the described embodiments have superior weight advantages over conventional type inner cowl structures. The de

50、sign of the apron structure allows for decoupling of the inner cowl structure from the pylon or pylon bracket, removing the need for the pylon to bare the structural loads and displacement challenges of the inner cowl due to engine thrust and aerodynamic forces. Moreover, the lower temperatures on t

51、he pylon, as explained above, alsoUS 2014/0319269 A1Oct. 30, 20143allow for lighter materials to be used leading to lighter and simplified structures without displacing weight to another area ofa propulsion system. Thus the pylon and pylon bracket may be designed, developed, and machined in alternat

52、e, lighter materials that are no longer required to withstand the forces or thermal loads that would otherwise be applied at pylon interfaces.0029 Yet another advantage that may be realized in the above embodiments is that the apron structure also provides a simpler means for sealing the inner cowl

53、about the engine. The sealing of the inner cowl additionally reduces fan duct leakage ofthe engine, which will have a direct effect to engine fuel consumption.0030 When designing aircraft components, important factors to address are size and weight. The above described advantages of the inner cowl s

54、tructure results in a lower weight, smaller sized, and increased performance engine sys tem. Reduced weight and size correlate to competitive advan tages during flight.0031 This written description uses examples to disclose the invention, including the best mode, and also to enable any person skille

55、d in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended t

56、o be within the scope of the claims if they have structural elements that do not differ from the literal language ofthe claims, or ifthey include equivalent structural elements with insubstantial differences from the literal languages of the claims.What is claimed is:1. An inner cowl structure for c

57、ircumscribing at least a portion of a jet engine having at least one engine mount coupled to an engine pylon extending from an aircraft wing, the inner cowl structure comprising:an apron configured to mount directly to the engine inde pendent ofthe pylon and overly an upper portion of the jet engine

58、; andan inner body configured to circumscribe a portion of the jet engine not circumscribed by the apron;wherein the inner cowl body is coupled to the apron such that the resulting combination ofthe coupled apron and inner cowl body defines a hoop structure that is struc turally independent ofthe pylon and completely circum scribes at least a portion ofthe jet engine.2. The inner cowl structure of claim 1 wherein the apron comprises at least one opening through which a connection